Outboard insertion system of variable guide vanes or stationary vanes

Abstract

A method of assembling a gas turbine engine comprising the steps of providing a casing having an insertion aperture in its outer surface. A guide vane is inserted through the insertion aperture. The guide vane is secured to the outer surface of the casing such that the guide vane can be serviced from an outer part of the casing.

What is claimed is: 
     
       1. A method of assembling a gas turbine engine comprising the steps of:
 providing a casing, said casing having an insertion aperture in its outer surface; 
 providing a guide vane; 
 inserting said guide vane through said insertion aperture in said casing while said guide vane is in an insertion orientation; 
 rotating said guide vane from said insertion orientation to an operational orientation about a longitudinal axis of the guide vane after full insertion; and 
 securing said guide vane to the outer surface of said casing, wherein said guide vane can be serviced from an outer part of said casing. 
 
     
     
       2. The method of assembling a gas turbine engine as claimed in  claim 1 , further comprising:
 installing a guide vane housing to secure said guide vane to the outer surface, said guide vane housing configured to seal said insertion aperture. 
 
     
     
       3. The method of assembling a gas turbine engine as claimed in  claim 1 , wherein
 said guide vane comprises a static mount guide vane. 
 
     
     
       4. The method of assembling a gas turbine engine as claimed in  claim 1 , wherein
 said guide vane comprises a variable position guide vane. 
 
     
     
       5. The method of assembling a gas turbine engine as claimed in  claim 1 , further comprising:
 placing an external cooling system in fluid communication with said guide vane after insertion, said guide vane including a plurality of cooling channels formed therein. 
 
     
     
       6. The method of assembling a gas turbine engine as claimed in  claim 1 , further comprising:
 placing a pressurized fluid reservoir in fluid communication with said guide vane after insertion, said guide vane including a plurality of compressor wash nozzles formed therein. 
 
     
     
       7. A gas turbine engine comprising:
 a guide casing having an insertion aperture in its outer surface, the guide casing being positioned axially between and connected to a fore casing and an aft casing; 
 a guide vane configured to be inserted into said guide casing through said insertion aperture from outside said guide casing; and 
 a housing for securing said guide vane partially within said insertion aperture on the outer perimeter of said guide casing, said guide vane having a portion that is mounted in the air flow path of the gas turbine engine, 
 wherein said insertion aperture is configured such that said guide vane is inserted through said insertion aperture while said guide vane is in an insertion orientation and rotated from said insertion orientation to an operational orientation about a longitudinal axis of the guide vane after full insertion. 
 
     
     
       8. The gas turbine engine as claimed in  claim 7 , wherein
 said guide vane is rotated greater than 90 degrees between said insertion orientation and said operational orientation. 
 
     
     
       9. The gas turbine engine as claimed in  claim 7 , wherein
 said guide vane comprises a static mount guide vane. 
 
     
     
       10. The gas turbine engine as claimed in  claim 7 , wherein
 said guide vane comprises a variable position guide vane. 
 
     
     
       11. The gas turbine engine as claimed in  claim 7 , wherein
 said housing secures said guide vane to the outer surface, and said housing is configured to seal said insertion aperture to said outer surface. 
 
     
     
       12. The gas turbine engine as claimed in  claim 7 , further comprising:
 an external cooling system in fluid communication with said guide vane, said guide vane including a plurality of cooling channels formed therein. 
 
     
     
       13. The gas turbine engine as claimed in  claim 7 , further comprising:
 a pressurized fluid reservoir in fluid communication with said guide vane, said guide vane including a plurality of compressor wash nozzles formed therein. 
 
     
     
       14. A gas turbine engine comprising:
 a guide casing having an insertion aperture in its outer surface, the guide casing being positioned axially between and connected to a fore casing and an aft casing; 
 a guide vane configured to be inserted into said guide casing through said insertion aperture from outside said guide casing; and 
 a guide vane housing for securing said guide vane partially within said insertion aperture on the outer perimeter of said guide casing, said guide vane housing sealing said insertion aperture, 
 wherein said insertion aperture is configured such that said guide vane is inserted through said insertion aperture while said guide vane is in an insertion orientation and rotated from said insertion orientation to an operational orientation about a longitudinal axis of the guide vane after full insertion. 
 
     
     
       15. The gas turbine engine as claimed in  claim 14 , wherein
 said guide vane is rotated greater than 90 degrees between said insertion orientation and said operational orientation. 
 
     
     
       16. The gas turbine engine as claimed in  claim 14 , further comprising:
 a floating mount formed within an interior surface of said guide casing, said floating mount configured to engage one end of said guide vane. 
 
     
     
       17. The gas turbine engine as claimed in  claim 14 , further comprising:
 an external cooling system in fluid communication with said guide vane, said guide vane including a plurality of cooling channels formed therein. 
 
     
     
       18. The gas turbine engine as claimed in  claim 14 , further comprising:
 a pressurized fluid reservoir in fluid communication with said guide vane, said guide vane including a plurality of compressor wash nozzles formed therein.